Masking techniques for electrochemical stripping

Abstract

A maskant for use in an electrochemical stripping operation is provided. The maskant comprises an electrically conductive member, preferably one formed from a titanium based material, placed about a trailing edge of an airfoil portion of a turbine engine component. A method for removing a coating from a turbine engine component is also provided. The method comprises the steps of placing a maskant formed from an electrically conductive material, preferably a titanium based material, adjacent a trailing edge of an airfoil portion of the component, immersing the turbine engine component and the maskant into a bath, and electrochemically stripping the coating from unmasked portions of the turbine engine component.

1 . A maskant for use in an electrochemical stripping operation comprising an electrically conductive maskant placed about an edge of an airfoil portion of a turbine engine component.  
     
     
         2 . A maskant according to  claim 1 , wherein said maskant is formed from a titanium based material.  
     
     
         3 . A maskant according to  claim 2 , wherein said maskant comprises two bars of said titanium based material placed on opposite sides of said trailing edge and bolted together.  
     
     
         4 . A maskant according to  claim 2 , wherein said maskant comprises a clip formed from a titanium based material placed over said trailing edge portion.  
     
     
         5 . A maskant according to  claim 2 , wherein said maskant comprises a clip having a layer of insulating material and a pair of spaced apart plates placed over said insulating material layer, and wherein said plates are connected to each other by a hinge.  
     
     
         6 . A maskant according to  claim 5 , wherein said plates are each formed from a titanium based material.  
     
     
         7 . A maskant according to  claim 5 , further comprising at least one C-shaped securing member positioned over said plates.  
     
     
         8 . A method for removing a coating from an airfoil portion of a turbine engine component comprising: 
 placing a maskant formed from an electrically conductive material on opposed sides of an edge of said airfoil portion;    immersing said turbine engine component with said maskant into a bath; and    electrochemically stripping a coating from unmasked portions of said turbine engine component.    
     
     
         9 . A method according to  claim 8 , further comprising applying a UV curable material to at least one side of said trailing edge prior to said maskant placing step and placing said maskant over said UV curable material.  
     
     
         10 . A method according to  claim 8 , wherein said maskant placing step comprises placing a maskant formed from a titanium based material on opposed sides of said trailing edge.  
     
     
         11 . A method according to  claim 8 , wherein said maskant placing step comprises placing two bars formed from a titanium based material on opposed sides of said trailing edge and bolting said bars together.  
     
     
         12 . A method according to  claim 8 , wherein said maskant placing step comprises placing a clip formed from a titanium based material on opposed sides of said trailing edge and securing said clip to said trailing edge.  
     
     
         13 . A method according to  claim 8 , wherein said maskant placing step comprises placing a clip having a layer of insulating material and a pair of plates each formed from a titanium based material on opposed sides of the trailing edge and securing said clip to said trailing edge.  
     
     
         14 . A method according to  claim 8 , further comprising placing a maskant on root portions of said turbine engine component.  
     
     
         15 . A method according to  claim 14 , wherein said root portion masking step comprises applying a masking paint.  
     
     
         16 . A method according to  claim 14 , wherein said root portion masking step comprises applying a lacquer to said root portions.  
     
     
         17 . A system for masking a portion of a turbine engine component during an electrochemical strip operation, said system comprising: 
 a UV curable material placed on an edge portion of said turbine engine component; and    an electrically conductive member placed over said UV curable material.    
     
     
         18 . The system according to  claim 17 , wherein said electrically conductive member is formed from a titanium based material.  
     
     
         19 . The system according to  claim 18 , wherein said electrically conductive member comprises two bars of a titanium based material placed in opposite sides of said trailing edge.  
     
     
         20 . The system according to  claim 18 , wherein said electrically conducive member comprises a clip formed from a titanium based material placed over said trailing edge portion.  
     
     
         21 . The system according to  claim 17 , further comprising means for masking root portions of said turbine engine component.  
     
     
         22 . The system according to  claim 21 , wherein said masking means comprises paint applied to said root portions.  
     
     
         23 . The system according to  claim 21 , wherein said masking means comprises lacquer applied to said root portions.